Aircraft accessory drive system

Patent metadata

Field	Value
Publication number	US-12012900-B2
Application number	US-202318302096-A
Country	US
Kind code	B2
Filing date	Apr 18, 2023
Priority date	May 3, 2022
Publication date	Jun 18, 2024
Grant date	Jun 18, 2024

Abstract

Disclosed is an aircraft accessory drive system comprising: a drive shaft configured to provide a drive input; a critical accessory directly coupled to the drive shaft so as to be directly driven by the drive shaft; a parasitic drive system configured to transmit drive input from the drive shaft to one or more less critical accessories, wherein the parasitic drive system comprises a torque limiter configured to decouple the parasitic drive system from the drive shaft and the critical accessory in response to a jam affecting the parasitic drive system or one or more of the less critical accessories. Also disclosed are a gas turbine engine comprising an aircraft accessory drive system, and an aircraft comprising an aircraft accessory drive system.

First claim

What is claimed is:

1. An aircraft accessory drive system comprising:
a drive shaft configured to provide a drive input;
an electric motor, and wherein the drive shaft is configured to be driven by the electric motor;
a first accessory directly coupled to the drive shaft so as to be directly driven by the drive shaft;
a parasitic drive system configured to transmit drive input from the electric motor to an at least one additional accessory, wherein the parasitic drive system comprises a torque limiter configured to decouple the parasitic drive system from the electric motor in response to a jam affecting the parasitic drive system or the at least one additional accessory, and
wherein the parasitic drive system comprises a parasitic drive shaft configured to be driven by the electric motor, and the torque limiter is disposed on the parasitic drive shaft.

2. The aircraft accessory drive system as claimed in claim 1 , wherein the parasitic drive shaft is configured to pass-through the first accessory.

3. The aircraft accessory drive system as claimed in claim 1 , wherein the parasitic drive shaft is configured to pass-through a mounting interface or a mounting adaptor.

4. The aircraft accessory drive system as claimed in claim 1 , wherein the torque limiter is a sacrificial part configured to break and to decouple the parasitic drive system from the drive shaft and the first accessory.

5. The aircraft accessory drive system as claimed in claim 4 , wherein the sacrificial part is configured to break at a predetermined torque, and wherein the predetermined torque is less than a failure torque of a coupling between the first accessory and the drive shaft.

6. The aircraft accessory drive system as claimed in claim 1 , wherein the torque limiter is a shear neck in the parasitic drive shaft of the parasitic drive system.

7. The aircraft accessory drive system as claimed in claim 1 , wherein the parasitic drive system is configured to drive a gearbox to which the at least one additional accessory is coupled.

8. The aircraft accessory drive system as claimed in claim 1 , wherein the first accessory is a pump, optionally a fuel pump or an oil pump.

9. A gas turbine engine for an aircraft, the gas turbine engine comprising the aircraft accessory drive system as claimed in claim 1 .

10. The gas turbine engine of claim 9 , further comprising:
an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor;
a fan located upstream of the engine core, the fan comprising a plurality of fan blades; and
a gearbox that receives an input from the core shaft and outputs drive to the fan so as to drive the fan at a lower rotational speed than the core shaft.

11. The gas turbine engine according to claim 10 , wherein:
the turbine is a first turbine, the compressor is a first compressor, and the core shaft is a first core shaft;
the engine core further comprises a second turbine, a second compressor, and a second core shaft connecting the second turbine to the second compressor; and
the second turbine, second compressor, and second core shaft are arranged to rotate at a higher rotational speed than the first core shaft.

12. An aircraft comprising:
the aircraft accessory drive system as claimed in claim 1 ;
a gas turbine engine.

Assignees

• Rolls Royce Plc

Inventors

• Cartwright Matthew S
• Yeandel Michael

Classifications

• F02C7/36

  Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user ({F02C3/107 - F02C3/13 and} F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H) · CPC title

• B64D2041/002

  Mounting arrangements for auxiliary power units (APU's) · CPC title

• B64D41/00

  Power installations for auxiliary purposes · CPC title

• F05D2270/09

  to cope with emergencies · CPC title

• F02C7/32 Primary

  Arrangement, mounting, or driving, of auxiliaries · CPC title